Aeroplane.



M. SEYMOUR.

AEROPLANE.

APPLICATION FILED JAN. 2. 1911.

1,326,535. Patented Dec. 30,1919.

3 SHEETS-SHEET I.

M. SEYMOUR.

AEROPLANE.

, APPLICATION FILED JAN.2. 1917.

1,326,535. Patented Dec. 30,1919.

3 SHEETSSHEET 2- M. SEYMOUR.

AEROPLANE.

APPLICATION FILED 1AN. 2. 1917.

Patented Dec. 30, 1919.

3 SHEETS-SHEET 3.

UNTTED STATES PATENT OFFICE.

MALCOLM SEYMOUR, F BOSTGN, MASSACHUSETTS.

AEROPLANE.

Application filed January 2, 1317.

To all whom it may concern:

Be it known that I, lviimcomi SnYnoUR, a citizen of the United States,residing at Boston, county of Suffolk, Commonwealth of lvLlassachusetts,have invented certain new and useful Improvements in Aeroplanes, of

. fully described in the specification which follows, and particularlypointed out in the appended claim. Throughout the specification anddrawings like reference characters are correspondingly applied, and inthe drawings Figure 1 is a plan view of an aeroplane in accordance withmy invention,

Fig. 2 is an elevation, partly in longitudinal section thereof.

Fig. 3 is a bow view, and

Fig. 1 is a stern view.

I have indicated at 1 a frame member or keel to which is braced a sternpiece 2 and propeller frame 8. The frame member 1 which I term the keelon account of its relation to the body of the machine is inclined foreand aft, and forms the lower edge of an elongated pyramidal frame oftriangular cross section. The longitudinal edge frames l le are suitablybraced to each other and to the keel member 1 as at 21 to providecentrally of the plane spread proper a light braced structure or body ofgreat strength and rigidity.

The body thus defined by the longitudinal frames 1, l--i and the braces21, is covered on its two lower faces with a suitable surfacing S whichis continued as at S to form the wing planes. The wing planes aredefined by the edge frames l-it, the rear cross frame 5 which with therear braces 21 constitute a triangular stern frame for the body andstringers drawn from the ends of the cross frame 5 to the apex or bow 6of the body. These wings or laterals are substantially elongatedtriangles and are set in the plane of the top frames of the body.

The ascent and descent of the machme 1S controlled through a pair ofhorizontal steering rudders 7 hinged to the cross frame Specification ofLetters Patent.

Patented Dec. 30, 1919.

Serial No. 140,668.

5 and thus disposed at the rear ends of the wings or laterals formed bythe surfaces S The horizontal rudders 7 are moved upwardly anddownwardly by a control 8 within convenient reach of the pilot. I

The horizontal rudder connections 9 extend over suitable sheaves in abraced frame 11 mounted in the cross frame 5 to a drum 8 on the shaft ofthe wheel 8 being guided along the frame in suitable sheaves 11 Thecontrol 8 as here shown is a simple hand wheel mounted on a transversedrum shaft provided with the drum. 8 over which the control lines areturned and run as described to the opposite sides of the rudder 7 givingan opposed control. These connec tions enable the pilot to tilt eitherhorizontal rudders 7 upwardly or downwardly as indicated in dottedlines, Fig. 2.

ll ithin the body framework of the machine is set the motor 12 fordriving a propeller 13. The fuel tank 145 may be mounted in anyconvenient part of the pyramidal frame and the drivers seat 15 may beconveniently located in the waist of the body, all being preferablydisposed to secure the desired balance.

The engine control, not indicated, n'ia-ybe suitably connected accordingto engine type and installation.

The lateral movements of the machine are guided by vertical fins orrudders 16 hinged to a second cross frame 5 which crosses the centralbody of the machine at the second angular body frame 21, thus forming acomplete triangular body frame at this point. Second cross frame 5 isextended as is the frame 5 to the full width of the lateral planes atthat point. The vertical rudders 16 are operated by control lines 1'?passing over sheaves 18 to a control wheel 19. The control wheel 19 ison a shaft having a drum 20 about which the line 17 is turned.

Corresponding with the cross frames 5 and 5 at the next forward frame ofthe body is disposed a cross member 5 similarly mounted and similarlybracing the body. Connecting the ends of these members 5, 5 and 5 ispreferably a rigid stringer 22. This is not essential, but is preferredconstruction, it braces the area of the wing in which the ruddercontrols are located, and strengthens the broader areas of the laterals.The base of the laterals are also traced by wire braces 28 which aredrawn taut to the rear end of the keel member 1.

The laterals are preferably strung forward of the cross frame 5 at leastwith fore and aft bracing wires 2a drawn from the cross frames atsuitable distances from the body of the car to the apex or bow 6 of thebody. This not only aifords a light form of body bracing, butstrengthens the wing planes and gives reinforced bearing surface.

Referring to Figs. 1 and 3 I preferably provide a wheel base as follows:I provide a rear wheel frame 25 attached directly to the keel member 1having a wheel 26 and a forward wheel support 27 constituting aplurality of braces running from the keel member 1 and the adjacentlateral ribs 21 which form the V-shaped frame of the body portion. Thesesupports carry preferably a pair of wheels 28.

In constructing my machine I dispose my engine tank, fuel tank, pilotslocation, controls and gear so as to bring the center of gravity of themachine when flown slightly in advance of the transverse center of theplane spread so as to bring a preponderance of plane surface to the rearof the center of gravity. z

This phase of my invention, while in part combining with the particularplane disposition of my machine is in itself believed to be an elementof novelty and to involve important principles. Without committingmyself to theories, I may point out certain features and results in theaction of such a machine in the air which are elements of greatadvantage.

The combination of gravity center with slightly predominating effectiveplane spread gives to the machine an unusual stability both on thelateral wing and in flight. By proportioning the fore and aft planespread relative to the center of gravity, I am able to produce a machinewhich will carry its rear with least strain, which will glide, even froma moment of substantial arrest in its flight, and which is veryresponsive to its controls.

Various modifications may be made in the shapes and proportion of partsand details of structures, all without departing from the spirit of myinvention if within the limits of the appended claim.

lVhat I therefore claim and desire to secure by Letters Patent is:

In flying apparatus, a triangular pyramidal central frame, spacedangular body braces therefor, a pair of forwardly tapering triangularwings arranged in co-planar relation to and in common apex with saidcentral frame, transverse frames crossing the central frame at saidangular body braces therefor, and extended to the full width of thelateral wings and forming with said angular braces complete triangularbody bracing frames, directive elements mounted on said transverseframes at either side of the central frame, and propulsive and controlequipment mounted upon said central frame.

In testimony whereof I aiiix my signature in presence of two witnesses.

MALCOLM SEYMOUR. Witnesses:

VICTORIA LOWDEN,

MARY P. Wo'rHERsrooN.

